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1.发明申请公开(公告)号：US20190219266A1
公开(公告)日：2019-07-18
申请号：US16238660
申请日：2019-01-03
发明人： Dennis M. Moura , Carey Clum
CPC分类号： F23R3/06 , F01D25/12 , F05D2260/201 , F05D2260/202 , F05D2260/607 , F23R3/002 , F23R3/005 , F23R2900/00004 , F23R2900/03041 , F23R2900/03043 , F23R2900/03044
摘要： A gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface; a second component having an first surface oriented towards the second surface of the first component, a second surface opposite the first surface of the second component, and a cooling hole extending from the second surface of second component to the first surface of second component, wherein the second surface of the first component and the first surface of the second component define a cooling channel therebetween, and wherein the second component has a variable thickness along a first length of the second component, the variable thickness being configured to adjust a distance between the first surface of the second component and the second surface of the first component throughout the first length such that a Mach number of a cross airflow within the cooling channel is adjusted.
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公开(公告)号：US20190040745A1
公开(公告)日：2019-02-07
申请号：US15667765
申请日：2017-08-03
发明人： Emily Rosette Clark , James Richard Winka , Daniel Robinson Getsinger , Thomas Earl Dyson , Brian Gene Brzek , James Fredric Wiedenhoefer , William Robb Stewart
CPC分类号： F01D5/186 , F01D5/187 , F01D9/065 , F01D25/14 , F01D25/24 , F05D2240/11 , F05D2240/303 , F05D2240/304 , F05D2250/314 , F05D2250/75 , F05D2260/202 , F05D2260/204 , F05D2260/205 , F05D2260/2212 , F05D2260/2214 , F23R3/002 , F23R3/005 , F23R3/06 , F23R2900/03041 , F23R2900/03045
摘要： An apparatus and method for cooling an engine component, such as an airfoil, for a turbine engine including an outer wall separating a cooling fluid flow from a hot fluid flow. A cooling circuit including a cooling passage having opposing sidewalls can be provided in the engine component. At least one turbulator can be provided between the opposing sidewalls, and can include a conduit having an inlet and an outlet passing through the at least one turbulator.
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公开(公告)号：US20180347373A1
公开(公告)日：2018-12-06
申请号：US16000239
申请日：2018-06-05
CPC分类号： F01D5/186 , F01D9/02 , F01D9/041 , F01D11/08 , F01D25/12 , F04D29/526 , F04D29/5846 , F05D2220/32 , F05D2230/21 , F05D2230/30 , F05D2250/28 , F05D2260/202 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , Y02T50/673 , Y02T50/676
摘要： A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a hollow vascular engineered lattice structure formed inside of the wall. The hollow vascular engineered lattice structure has an inlet hole and an outlet hole that communicate fluid into and out of the hollow vascular structure. The hollow vascular engineered lattice structure further has at least one resupply inlet hole between the inlet hole and the outlet hole with respect to a dimension of the component to communicate additional fluid into the hollow vascular engineered lattice structure.
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公开(公告)号：US20180335212A1
公开(公告)日：2018-11-22
申请号：US15599196
申请日：2017-05-18
发明人： SAN QUACH , JEFFREY T. MORTON
CPC分类号： F23R3/002 , F02C7/18 , F05D2220/32 , F05D2230/00 , F05D2240/35 , F05D2260/201 , F23R3/42 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
摘要： A combustor panel may include a body having an edge, a first endrail disposed along the edge of the body, and a second endrail disposed adjacent the first endrail, wherein a volume is defined between the first endrail and the second endrail. The first endrail may have a first height, measured from the body to a first tip of the first endrail, and the second endrail may have a second height, measured from the body to a second tip of the second endrail, wherein the first height is the same as the second height. The second endrail may include an endrail hole extending through the second endrail.
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公开(公告)号：US20180320595A1
公开(公告)日：2018-11-08
申请号：US15769193
申请日：2016-10-28
发明人： Kenji SATO , Kentaro TOKUYAMA
CPC分类号： F02C7/18 , F01D5/082 , F01D9/023 , F01D25/14 , F05D2240/35 , F23R3/06 , F23R3/42 , F23R3/50 , F23R2900/03041
摘要： In a combustion cylinder, gas turbine combustor, and gas turbine, an outer-side region of a cooling part which is a region on an outer side with regard to a reference line that is a straight line orthogonal to a radial direction and an axial direction of a gas turbine and passing through a center of a combustor basket, and an inner-side region of the cooling part which is a region on an inner side with regard to the reference line are set. A connection angle at an intersection between an extension line of an outer surface of the combustor basket along the axial direction and an inner surface of a combustor transition piece is set. First regions set at positions near the reference line in either the outer-side region or the inner-side region, and second regions with a larger connection angle than the first regions, set at positions farther from the reference line than the first regions are set. The second regions are set to have a higher flow rate of a cooling medium than the first regions.
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公开(公告)号：US20180306113A1
公开(公告)日：2018-10-25
申请号：US15491047
申请日：2017-04-19
发明人： Jeffrey T. Morton , San Quach
CPC分类号： F23R3/002 , F23R3/06 , F23R3/50 , F23R2900/00017 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044
摘要： A combustor section of a turbine engine includes a first liner panel including a first end rail. The first end rail includes a protruding heat transfer feature. A second liner panel includes a second end rail disposed proximate the first end rail. The second end rail includes a recess matching the protruding heat transfer feature of the first end rail. A turbine engine and a method of assembling a combustor assembly of a gas turbine engine are also disclosed.
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公开(公告)号：US10072846B2
公开(公告)日：2018-09-11
申请号：US14791684
申请日：2015-07-06
发明人： Sarah Marie Monahan , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Matthieu Marc Masquelet
IPC分类号： F23R3/28 , F23R3/34 , F23C5/08 , F23R3/58 , F23R3/12 , F23R3/04 , F23C5/00 , F23R3/42 , F23C5/32 , F23R3/02 , F23R3/10 , F23C5/24 , F23R3/06
CPC分类号： F23R3/286 , F05D2240/35 , F23C5/00 , F23C5/08 , F23C5/10 , F23C5/24 , F23C5/32 , F23R3/02 , F23R3/04 , F23R3/045 , F23R3/06 , F23R3/10 , F23R3/12 , F23R3/34 , F23R3/346 , F23R3/42 , F23R3/58 , F23R2900/00015 , F23R2900/03041 , F23R2900/03042 , Y02T50/675
摘要： A gas turbine engine and combustor assembly including a combustor liner defining therein a combustion chamber for the downstream flow of a main fluid. At least two axially spaced apart annular trapped vortex cavities are located on the combustor liner and staged axially and radially spaced apart. A cavity opening is located at a radially inner end of each of the at least two annular trapped vortex cavities. A plurality of injectors are configured tangentially relative to circular radially outer wall extending between an aft wall and a forward wall of each cavity to provide for an injection of air and fuel to form an annular rotating trapped vortex of a fuel and air mixture within a respective annular trapped vortex cavity. The annular rotating trapped vortex of the fuel and air mixture at the cavity openings is substantially perpendicular to the downstream flow of the main fluid.
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8.发明申请公开(公告)号：US20180231250A1
公开(公告)日：2018-08-16
申请号：US15348639
申请日：2016-11-10
发明人： Steven W. Burd
CPC分类号： F23M5/04 , F01D9/023 , F23M5/085 , F23R3/002 , F23R3/06 , F23R3/50 , F23R3/60 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
摘要： A combustor for a gas turbine engine including a forward liner panel mounted to a support shell via a multiple of studs, the forward liner panel including an aft non-linear circumferential edge and an aft liner panel mounted to the support shell via a multiple of studs, the aft liner panel including a forward non-linear circumferential edge that is complementary to the aft non-linear circumferential edge.
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公开(公告)号：US10001018B2
公开(公告)日：2018-06-19
申请号：US14063131
申请日：2013-10-25
CPC分类号： F01D5/188 , F01D5/187 , F01D25/12 , F05D2260/201 , F05D2260/204 , F05D2260/2214 , F23M5/085 , F23R3/005 , F23R2900/03041 , F23R2900/03045
摘要： The present application provides a hot gas path component for use in a hot gas path of a gas turbine engine. The hot gas path component may include an internal wall, an external wall facing the hot gas path, an impingement wall, a number of internal wall pedestals positioned between the internal wall and the impingement wall, and a number of external wall pedestals positioned between the external wall and the impingement wall.
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公开(公告)号：US09958160B2
公开(公告)日：2018-05-01
申请号：US14765222
申请日：2014-02-04
发明人： James A. Dierberger
CPC分类号： F23R3/06 , F01D25/12 , F01D25/30 , F05D2260/202 , F05D2260/4031 , F23R3/002 , F23R3/005 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044 , Y02T50/676
摘要： A component within a gas turbine engine includes a surface with one or more upstream-directed cooling film holes therethrough.
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